Airworthiness Directive · Amendment 39-18333 · Stabilizers
Airbus Airplanes
This AD applies to all airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A330-201, -202, -203, -223, -223F,-243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all manufacturer serial numbers.
(2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes, all manufacturer serial numbers.
We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340- 300, A340-500, and A340-600 series airplanes. This AD was prompted by a report of skin disbonding on a composite side panel of a rudder installed on an A310 airplane. This AD requires a review of the maintenance records of the rudder to determine if any composite side shell panel repair has been done; a thermography inspection limited to the repair areas or complete side shells, as applicable, to identify possible in-service rudder repairs, damages, or fluid ingress; and applicable related investigative and corrective actions. We are issuing this AD to detect and correct the rudder skin disbonding, which could affect the structural integrity of the rudder, and could result in reduced controllability of the airplane.
Within 24 months after the effective date of this AD: Review the maintenance records of the rudder to determine if any composite side shell panel repair has been accomplished on the rudder since first installation on an airplane.
(1) If, based on the maintenance record review, any repair identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD is found: Within 24 months after the effective date of this AD, do a thermography inspection for repair, damages, and fluid ingress, limited to the repaired areas, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD:
(i) Airbus Service Bulletin A330-55-3043, Revision 1, dated August 20, 2014 (for Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes).
(ii) Airbus Service Bulletin A340-55-4039, Revision 1, dated August 20, 2014 (for Model A340-211, -212, -213, -311, -312, and -313 airplanes).
(iii) Airbus Service Bulletin A340-55-5007, Revision 1, dated August 20, 2014 (for Model A340-541 and -642 airplanes).
(2) For a rudder for which maintenance records are unavailable or incomplete, do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD:
(i) No later than 3 months before accomplishment of the thermography inspection, as required by paragraph (g)(2)(ii) of this AD, contact Airbus to request related rudder manufacturing data by submitting the serial number of the rudder to Airbus.
(ii) Within 24 months after the effective date of this AD: Do a thermography inspection for any repair on complete side shells to identify and mark any repair, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD.
After the inspection as required by paragraph (g)(1) or (g)(2) of this AD: At the applicable compliance times specified in paragraph 1.E., “Compliance,” of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, accomplish all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD; except as provided by paragraphs (i)(1) and (i)(2) of this AD. Options provided in the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD for accomplishing the actions are acceptable for the corresponding requirements of this paragraph provided that the related investigative and corrective actions are done at the applicable times specified in paragraph 1.E., “Compliance,” of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, including applicable repetitive inspection intervals, except as required by paragraphs (i)(1) and (i)(2) of this AD. Thereafter repeat the inspections of the restored and repaired areas at the applicable compliance time specified in paragraph 1.E., “Compliance,” of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD.
(1) Where the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies a compliance time relative to the date of the service information, this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) If the service information in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies to contact Airbus: At the applicable compliance times specified in paragraph 1.E., “Compliance,” of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
Airplanes fitted with a rudder having a serial number (S/N) that is not in the range of S/N TS-1001 through S/N TS-1043 inclusive, S/N TS-2001 through S/N TS-2074 inclusive, S/N TS-3000 through S/N TS-3525 inclusive, S/N TS-4001 throughS/N TS-4170 inclusive, S/N TS-6001 through S/N TS-6246 inclusive, or S/N TS-5001 through S/N TS-5138 inclusive, are not affected by the requirements of paragraphs (g) and (h) of this AD provided that it is determined that no repair has been accomplished as described in the procedures identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable, on the composite side shell panel of that rudder since first installation on an airplane.
As of the effective date of this AD, no person may install, on any airplane, a rudder, unless the record review and thermography inspection specified in paragraph (g) of this AD has been done on that rudder and thereafter all applicable related investigative actions, repetitive inspections, and corrective actions are done as required by paragraph (h) of this AD, except as provided in paragraph (j) of this AD.
As of the effective date of this AD, no person may accomplish a side shell repair on any rudder using a structure repair manual procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable, on any airplane.
